US3314651A - Sealing device - Google Patents

Sealing device Download PDF

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Publication number
US3314651A
US3314651A US440714A US44071465A US3314651A US 3314651 A US3314651 A US 3314651A US 440714 A US440714 A US 440714A US 44071465 A US44071465 A US 44071465A US 3314651 A US3314651 A US 3314651A
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Prior art keywords
fixed structure
rotor
sealing
sealing rib
blades
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Expired - Lifetime
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US440714A
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Richard D Beale
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Rolls Royce PLC
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Rolls Royce PLC
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61K—PREPARATIONS FOR MEDICAL, DENTAL OR TOILETRY PURPOSES
    • A61K8/00—Cosmetics or similar toiletry preparations
    • A61K8/18—Cosmetics or similar toiletry preparations characterised by the composition
    • A61K8/30—Cosmetics or similar toiletry preparations characterised by the composition containing organic compounds
    • A61K8/49—Cosmetics or similar toiletry preparations characterised by the composition containing organic compounds containing heterocyclic compounds
    • A61K8/4906—Cosmetics or similar toiletry preparations characterised by the composition containing organic compounds containing heterocyclic compounds with one nitrogen as the only hetero atom
    • A61K8/4913—Cosmetics or similar toiletry preparations characterised by the composition containing organic compounds containing heterocyclic compounds with one nitrogen as the only hetero atom having five membered rings, e.g. pyrrolidone carboxylic acid
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61Q—SPECIFIC USE OF COSMETICS OR SIMILAR TOILETRY PREPARATIONS
    • A61Q15/00—Anti-perspirants or body deodorants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/445—Free-space packings with means for adjusting the clearance

Definitions

  • an axial flow rotor fixed structure within which the rotor is rotatably mounted, said fixed structure being provided with a plurality of surfaces which are inclined at acute angles to the axis of the rotor, a plurality of radially extending blades on the rotor, at least one radially extending sealing rib and at least one axially extending sealing rib on the radially outer end of each blade, each said sealing rib being adapted to make a seal with at least one said surface of said fixed structure, at least one of said sealing ribs on each blade being at all times in sealing contact With a respective surface of the fixed structure even when relative radial and axial movement has occurred between the blades and the fixed structure.
  • Each of the sealing ribs and the fixed structure are preferably made of materials such that each sealing rib can cut a path for itself in the respective surface.
  • the axially extending ribs preferably extend upstream of the rotor blades.
  • the rotor may be a turbine for a gas turbine engine.
  • FIGURE 1 is a diagrammatic view, partly in section, of a gas turbine engine provided with a rotor according to the present invention
  • FIGURE 2 as a broken-away sectional view on a larger scale of part of the structure shown in FIGURE 1, and
  • FIGURE 3 is a broken-away sectional view on a yet larger scale of part of the structure shown in FIGURE 2, certain parts being shown in FIGURE 3 in a number of different positions.
  • FIGURE 1 there is shown a gas turbine jet engine adapted for use in aircraft propulsion, the engine 10 comprising an engine casing 11 Within which there are mounted in flow series a compressor 12, combustion equipment 13 and a turbine 14, the turbine exhaust gases being directed to atmosphere through an exhaust duct 15.
  • the engine 10 comprising an engine casing 11 Within which there are mounted in flow series a compressor 12, combustion equipment 13 and a turbine 14, the turbine exhaust gases being directed to atmosphere through an exhaust duct 15.
  • An annular member 16 (see FIGURE 2) is mounted within the engine casing 11 and is provided on its radially inner side with an annular assembly of inserts 17.
  • Each of the inserts 17 (see FIGURE 3) is provided with substantially axial inclined surfaces 20, 21 and with substantially radial inclined surfaces 22, 23, 24. Each of the surfaces 20, 21, 23 and 24 is inclined at an acute angle to the axis of the turbine 14.
  • the turbine 14 has a plurality of rotor blades 25.
  • Each of the rotor blades 25 has a shroud 26 which is formed with radially extending sealing ribs 30, 31, 32, and with an axially extending sealing rib 33.
  • the sealing rib 30 When the engine 10 is not in operation, the sealing rib 30 is in the position indicated at 30a in FIGURE 3, in which it makes sealing contact with the downstream end of the axial inclined surface 20, whilst the axially extending sealing rib 33 is in the position indicated at 33a, where it is spaced from the radial inclined surfaces 22,
  • the turbine 14 When the engine 10 is running at ground idling speed, the turbine 14 will expand radially with respect to the casing 11, whilst the latter will expand axially.
  • the radially extending sealing rib 30 will thus, in effect, move upstream along the axial inclined surface 20 so as to adopt the position shown at 30b, in which it makes sealing contact with the axial inclined surface 20.
  • the axially extending sealing rib 33 will be disposed at the position shown at 33b, in which it will be well spaced from any of the radial inclined surfaces 22 to 24.
  • the engine casing 11 When the engine 10 is being operated at cruise speeds, the engine casing 11 will expand both radially and axially with respect to the turbine 14, and the radially extending sealing rib 30 will then be disposed in the position indicated at 300, where it will be well spaced from the axial inclined surface 20. At this time, however, the axial inclined surface 33 will be disposed as shown at 33c in sealing contact with the radial inclined surface 24.
  • the radially extending sealing rib 30 and the axially extending sealing rib 33 are disposed in the positions indicated at 30d, 33d respectively. In these positions, the radially extending sealing rib 30 is spaced away from the axial inclined surface 20, whilst the axially extending sealing rib 33 is disposed in sealing contact with the radial inclined surfaces 23, 24.
  • the radially extending sealing rib 30 When the engine 10 is being run at speeds corresponding to rapid starting and slam acceleration, the radially extending sealing rib 30 will be disposed in the position indicated at 302, where it makes sealing contact with the axial inclined surfaces 20, 21. Moreover, at this time the axially extending sealing rib 33 will be disposed at the position indicated at 33e, in which it contacts the radial inclined surface 22.
  • the blades 25 are made of a nickel-based alloy, such as that sold under the Registered Trademark Nimonic, whilst the inserts 17 are made of cast iron, or of other material such as to permit the sealing ribs 30, 33, to cut paths for themselves in the surfaces of the inserts 17 if this should be necessary on relative expansion and contraction of the parts.
  • An axial flow rotor, fixed structure within which the rotor is rotatably mounted said fixed structure being provided with a plurality of surfaces which are inclined at acute angles to the axis of the rotor, a plurality of radially extending blades on the rotor, at least one radially extending sealing rib and at least one axially extending sealing rib on the radially outer end of each blade, each said sealing rib being adapted to make a seal with at least one of said surfaces of said fixed structure, at least one of said sealing ribs on each blade being at all times in sealing contact with a respective surface of the fixed structure even when relative radial and axial movement has occurred between the blades and the fixed structure.
  • An axial flow rotor, fixed structure within which the rotor is rotatably mounted said fixed structure being provided with a plurality of surfaces which are inclined at acute angles to the axis of the rotor, a plurality of radially extending blades on the rotor, at least one radially extending sealing rib and at least one axially extending seal- 3 d ing rib on the radially outer end of each blade, each said the fixed structure even when relative vradial and axial sealing rib being adapted to make a seal with at least one movement has occurred "between the blades and fixed of said surfaces of said fixed structure and each of the structure.
  • sealing ribs and the fixed structure being made of materials such that each sealing rib can cut a path for itself References Cited y the Examine! in the respective surface, at least one of said sealing ribs UNITED STATES PATENTS on each blade being at all times in sealing contact with a respective surface of the fixed structure even when relaf i I tive radial and axial movement has occurred between the or By at a blades and fixed structure.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Animal Behavior & Ethology (AREA)
  • Public Health (AREA)
  • Veterinary Medicine (AREA)
  • Birds (AREA)
  • Epidemiology (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Description

April 18, 1967 R D, BEALE 3,314,651
SEALING DEVICE Filed March 18, 1965 United States Patent Ofilice 3,314,651 Patented Apr. 18, 1967 Britain Filed Mar. 18, 1965, Ser. No. 440,714 Claims priority, application Great Britain, Apr. 9, 1964, 14,801/ 64 3 Claims. (Cl. 253-77) This invention concerns an axial flow rotor.
According to the present invention, there is provided an axial flow rotor, fixed structure within which the rotor is rotatably mounted, said fixed structure being provided with a plurality of surfaces which are inclined at acute angles to the axis of the rotor, a plurality of radially extending blades on the rotor, at least one radially extending sealing rib and at least one axially extending sealing rib on the radially outer end of each blade, each said sealing rib being adapted to make a seal with at least one said surface of said fixed structure, at least one of said sealing ribs on each blade being at all times in sealing contact With a respective surface of the fixed structure even when relative radial and axial movement has occurred between the blades and the fixed structure.
Each of the sealing ribs and the fixed structure are preferably made of materials such that each sealing rib can cut a path for itself in the respective surface.
The axially extending ribs preferably extend upstream of the rotor blades.
The rotor may be a turbine for a gas turbine engine.
The invention is illustrated, merely by way of example, in the accompanying drawings, in which:
FIGURE 1 is a diagrammatic view, partly in section, of a gas turbine engine provided with a rotor according to the present invention,
FIGURE 2 as a broken-away sectional view on a larger scale of part of the structure shown in FIGURE 1, and
FIGURE 3 is a broken-away sectional view on a yet larger scale of part of the structure shown in FIGURE 2, certain parts being shown in FIGURE 3 in a number of different positions.
In FIGURE 1 there is shown a gas turbine jet engine adapted for use in aircraft propulsion, the engine 10 comprising an engine casing 11 Within which there are mounted in flow series a compressor 12, combustion equipment 13 and a turbine 14, the turbine exhaust gases being directed to atmosphere through an exhaust duct 15.
An annular member 16 (see FIGURE 2) is mounted within the engine casing 11 and is provided on its radially inner side with an annular assembly of inserts 17.
Each of the inserts 17 (see FIGURE 3) is provided with substantially axial inclined surfaces 20, 21 and with substantially radial inclined surfaces 22, 23, 24. Each of the surfaces 20, 21, 23 and 24 is inclined at an acute angle to the axis of the turbine 14.
The turbine 14 has a plurality of rotor blades 25. Each of the rotor blades 25 has a shroud 26 which is formed with radially extending sealing ribs 30, 31, 32, and with an axially extending sealing rib 33.
When the engine 10 is not in operation, the sealing rib 30 is in the position indicated at 30a in FIGURE 3, in which it makes sealing contact with the downstream end of the axial inclined surface 20, whilst the axially extending sealing rib 33 is in the position indicated at 33a, where it is spaced from the radial inclined surfaces 22,
2 23, 24. In this position, the radially extending sealing Ill) 30 makes a seal with the axial inclined surface 20.
When the engine 10 is running at ground idling speed, the turbine 14 will expand radially with respect to the casing 11, whilst the latter will expand axially. The radially extending sealing rib 30 will thus, in effect, move upstream along the axial inclined surface 20 so as to adopt the position shown at 30b, in which it makes sealing contact with the axial inclined surface 20. At this time, the axially extending sealing rib 33 will be disposed at the position shown at 33b, in which it will be well spaced from any of the radial inclined surfaces 22 to 24.
When the engine 10 is being operated at cruise speeds, the engine casing 11 will expand both radially and axially with respect to the turbine 14, and the radially extending sealing rib 30 will then be disposed in the position indicated at 300, where it will be well spaced from the axial inclined surface 20. At this time, however, the axial inclined surface 33 will be disposed as shown at 33c in sealing contact with the radial inclined surface 24.
When the engine 10 is operated at takeoff speed, the radially extending sealing rib 30 and the axially extending sealing rib 33 are disposed in the positions indicated at 30d, 33d respectively. In these positions, the radially extending sealing rib 30 is spaced away from the axial inclined surface 20, whilst the axially extending sealing rib 33 is disposed in sealing contact with the radial inclined surfaces 23, 24.
When the engine 10 is being run at speeds corresponding to rapid starting and slam acceleration, the radially extending sealing rib 30 will be disposed in the position indicated at 302, where it makes sealing contact with the axial inclined surfaces 20, 21. Moreover, at this time the axially extending sealing rib 33 will be disposed at the position indicated at 33e, in which it contacts the radial inclined surface 22.
It will thus be appreciated that in all operative conditions, one or both of the sealing ribs 30, 33, will make a seal with one or more of the surfaces on the inserts 17.
The blades 25 are made of a nickel-based alloy, such as that sold under the Registered Trademark Nimonic, whilst the inserts 17 are made of cast iron, or of other material such as to permit the sealing ribs 30, 33, to cut paths for themselves in the surfaces of the inserts 17 if this should be necessary on relative expansion and contraction of the parts.
I claim:
1. An axial flow rotor, fixed structure within which the rotor is rotatably mounted, said fixed structure being provided with a plurality of surfaces which are inclined at acute angles to the axis of the rotor, a plurality of radially extending blades on the rotor, at least one radially extending sealing rib and at least one axially extending sealing rib on the radially outer end of each blade, each said sealing rib being adapted to make a seal with at least one of said surfaces of said fixed structure, at least one of said sealing ribs on each blade being at all times in sealing contact with a respective surface of the fixed structure even when relative radial and axial movement has occurred between the blades and the fixed structure.
2. An axial flow rotor, fixed structure within which the rotor is rotatably mounted, said fixed structure being provided with a plurality of surfaces which are inclined at acute angles to the axis of the rotor, a plurality of radially extending blades on the rotor, at least one radially extending sealing rib and at least one axially extending seal- 3 d ing rib on the radially outer end of each blade, each said the fixed structure even when relative vradial and axial sealing rib being adapted to make a seal with at least one movement has occurred "between the blades and fixed of said surfaces of said fixed structure and each of the structure.
sealing ribs and the fixed structure being made of materials such that each sealing rib can cut a path for itself References Cited y the Examine! in the respective surface, at least one of said sealing ribs UNITED STATES PATENTS on each blade being at all times in sealing contact with a respective surface of the fixed structure even when relaf i I tive radial and axial movement has occurred between the or By at a blades and fixed structure.
3. An axial flow rotor, fixed structure Within which the 10 FOREIGN PATENTS rotor is rotatably mounted, said fixed structure being pro- 560,545 7/1923 France vided With a plurality of surfaces which are inclined at 485,833 11/1929 Germany acute angles to the axis of the rotor a plurality of radially 55 11/1943 Great Britain extending blades on the rotor, at least one radially ex- 15 563,727 8/1944 Great Britain tending sealing rib and at least one axially upstream 804,922 11/1958 Great Britain extending sealing rib on the radially outer end of each 140,809 3/1961 Russia blade, each said sealing rib being adapted to make a seal with at least one of said surfaces of said fixed structure, MA I p SCHWADRON, Primary Examiner at least one of said sealing ribs on each blade being at 20 all times in sealing contact with a respective surface of EVERETT POWELL Exammer'

Claims (1)

1. AN AXIAL FLOW ROTOR, FIXED STRUCTURE WITHIN WHICH THE ROTOR IS ROTATABLY MOUNTED, SAID FIXED STRUCTURE BEING PROVIDED WITH A PLURALITY OF SURFACES WHICH ARE INCLINED AT ACUTE ANGLES TO THE AXIS OF THE ROTOR, A PLURALITY OF RADIALLY EXTENDING BLADES ON THE ROTOR, AT LEAST ONE RADIALLY EXTENDING SEALING RIB AND AT LEAST ONE AXIALLY EXTENDING SEALING RIB ON THE RADIALLY OUTER END OF EACH BLADE, EACH SAID SEALING RIB BEING ADAPTED TO MAKE A SEAL WITH AT LEAST ONE OF SAID SURFACES OF SAID FIXED STRUCTURE, AT LEAST ONE OF SAID SEALING RIBS ON EACH BLADE BEING AT ALL TIMES IN SEALING CONTACT WITH A RESPECTIVE SURFACE OF THE FIXED STRUCTURE EVEN WHEN RELATIVE RADIAL AND AXIAL MOVEMENT HAS OCCURRED BETWEEN THE BLADES AND THE FIXED STRUCTURE.
US440714A 1964-04-09 1965-03-18 Sealing device Expired - Lifetime US3314651A (en)

Applications Claiming Priority (1)

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GB14801/64A GB1008526A (en) 1964-04-09 1964-04-09 Axial flow bladed rotor, e.g. for a turbine

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Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3677660A (en) * 1969-04-08 1972-07-18 Mitsubishi Heavy Ind Ltd Propeller with kort nozzle
DE2943464A1 (en) * 1978-10-30 1980-05-14 Gen Electric GASKET DEVICE FOR A GAS TURBINE ENGINE
US4662820A (en) * 1984-07-10 1987-05-05 Hitachi, Ltd. Turbine stage structure
US4820119A (en) * 1988-05-23 1989-04-11 United Technologies Corporation Inner turbine seal
US5234318A (en) * 1993-01-22 1993-08-10 Brandon Ronald E Clip-on radial tip seals for steam and gas turbines
US5632598A (en) * 1995-01-17 1997-05-27 Dresser-Rand Shrouded axial flow turbo machine utilizing multiple labrinth seals
US6068443A (en) * 1997-03-26 2000-05-30 Mitsubishi Heavy Industries, Ltd. Gas turbine tip shroud blade cavity
US6102655A (en) * 1997-09-19 2000-08-15 Asea Brown Boveri Ag Shroud band for an axial-flow turbine
US20040253100A1 (en) * 2003-05-13 2004-12-16 Alstom Technology Ltd Axial flow steam turbines
US20090014964A1 (en) * 2007-07-09 2009-01-15 Siemens Power Generation, Inc. Angled honeycomb seal between turbine rotors and turbine stators in a turbine engine
US20090189356A1 (en) * 2007-12-14 2009-07-30 Miklos Gaebler Sealing of at least one shaft by at least one hydraulic seal
EP1676978A3 (en) * 2004-12-29 2009-09-02 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
US20110002777A1 (en) * 2009-07-02 2011-01-06 General Electric Company Systems and apparatus relating to turbine engines and seals for turbine engines
US20110229301A1 (en) * 2010-03-22 2011-09-22 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US20120091662A1 (en) * 2010-10-19 2012-04-19 General Electric Company Labyrinth seal system
US20140169972A1 (en) * 2012-12-17 2014-06-19 United Technologies Corporation Fan with integral shroud
US8876484B2 (en) 2011-08-05 2014-11-04 Hamilton Sundstrand Corporation Turbine blade pocket pin stress relief
US20150016985A1 (en) * 2013-07-12 2015-01-15 MTU Aero Engines AG Gas turbine stage
EP2886801A1 (en) * 2013-12-20 2015-06-24 Alstom Technology Ltd Seal system for a gas turbine and corresponding gas turbine
US20160305266A1 (en) * 2015-04-15 2016-10-20 United Technologies Corporation Seal configuration to prevent rotor lock
WO2017155497A1 (en) * 2016-03-07 2017-09-14 Siemens Aktiengesellschaft Gas turbine blade tip shroud sealing and flow guiding features
CN107605543A (en) * 2017-08-14 2018-01-19 西北工业大学 A kind of dividing disc cavity configuration for wheel rim sealing

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3401742C2 (en) * 1984-01-19 1986-08-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Rotor for an axial compressor
US4645417A (en) * 1984-02-06 1987-02-24 General Electric Company Compressor casing recess
US4909706A (en) * 1987-01-28 1990-03-20 Union Carbide Corporation Controlled clearance labyrinth seal
US4884820A (en) * 1987-05-19 1989-12-05 Union Carbide Corporation Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members
GB2310895A (en) * 1996-03-04 1997-09-10 Rolls Royce Plc Turbine shroud assembly
GB9717857D0 (en) * 1997-08-23 1997-10-29 Rolls Royce Plc Fluid Seal
DE10156193A1 (en) * 2001-11-15 2003-06-05 Alstom Switzerland Ltd Heat shield for gas turbine stator, has arrangement on shield to prevent hot air turbulence form forming in hollow volume upstream of first arrangement for preventing hot air flow.
GB2417053B (en) 2004-08-11 2006-07-12 Rolls Royce Plc Turbine
DE102009011297A1 (en) * 2009-03-02 2010-09-09 Rolls-Royce Deutschland Ltd & Co Kg Sealing arrangement for turbine of turbo machine, has groove comprising undercuts provided in axial direction, where platform and/or sealing ring comprise sealing element that engages groove and extends in peripheral direction
CN110662885B (en) * 2017-06-12 2022-04-01 三菱动力株式会社 Axial flow rotary machine

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FR560545A (en) * 1922-01-03 1923-10-05 Improvements to seals for rotating parts
DE485833C (en) * 1929-11-08 J A Maffei A G Process for the production of blades for turbo machines, in particular for steam or gas turbines
US1999739A (en) * 1934-03-24 1935-04-30 Westinghouse Electric & Mfg Co Removable packing strip
GB557490A (en) * 1941-05-24 1943-11-23 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
GB563727A (en) * 1942-03-12 1944-08-28 British Thomson Houston Co Ltd Improvements in and relating to sealing arrangements for elastic fluid turbines and the like
GB804922A (en) * 1956-01-13 1958-11-26 Rolls Royce Improvements in or relating to axial-flow fluid machines for example compressors andturbines
US3092393A (en) * 1958-01-20 1963-06-04 Rolls Royce Labyrinth seals

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CH267497A (en) * 1947-03-13 1950-03-31 Rolls Royce Gas turbine plant.

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE485833C (en) * 1929-11-08 J A Maffei A G Process for the production of blades for turbo machines, in particular for steam or gas turbines
FR560545A (en) * 1922-01-03 1923-10-05 Improvements to seals for rotating parts
US1999739A (en) * 1934-03-24 1935-04-30 Westinghouse Electric & Mfg Co Removable packing strip
GB557490A (en) * 1941-05-24 1943-11-23 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
GB563727A (en) * 1942-03-12 1944-08-28 British Thomson Houston Co Ltd Improvements in and relating to sealing arrangements for elastic fluid turbines and the like
GB804922A (en) * 1956-01-13 1958-11-26 Rolls Royce Improvements in or relating to axial-flow fluid machines for example compressors andturbines
US3092393A (en) * 1958-01-20 1963-06-04 Rolls Royce Labyrinth seals

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3677660A (en) * 1969-04-08 1972-07-18 Mitsubishi Heavy Ind Ltd Propeller with kort nozzle
DE2943464A1 (en) * 1978-10-30 1980-05-14 Gen Electric GASKET DEVICE FOR A GAS TURBINE ENGINE
FR2440474A1 (en) * 1978-10-30 1980-05-30 Gen Electric GAS TURBINE ENGINE WHOSE CRITICAL ELEMENTS OF THE ROTOR ARE PROTECTED AGAINST DIRECT CONTACT OF HOT GASES
US4309145A (en) * 1978-10-30 1982-01-05 General Electric Company Cooling air seal
US4662820A (en) * 1984-07-10 1987-05-05 Hitachi, Ltd. Turbine stage structure
US4820119A (en) * 1988-05-23 1989-04-11 United Technologies Corporation Inner turbine seal
US5234318A (en) * 1993-01-22 1993-08-10 Brandon Ronald E Clip-on radial tip seals for steam and gas turbines
US5632598A (en) * 1995-01-17 1997-05-27 Dresser-Rand Shrouded axial flow turbo machine utilizing multiple labrinth seals
US6068443A (en) * 1997-03-26 2000-05-30 Mitsubishi Heavy Industries, Ltd. Gas turbine tip shroud blade cavity
US6102655A (en) * 1997-09-19 2000-08-15 Asea Brown Boveri Ag Shroud band for an axial-flow turbine
US20040253100A1 (en) * 2003-05-13 2004-12-16 Alstom Technology Ltd Axial flow steam turbines
US7186074B2 (en) 2003-05-13 2007-03-06 Alstom Technology, Ltd. Axial flow stream turbines
EP1676978A3 (en) * 2004-12-29 2009-09-02 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
US20090014964A1 (en) * 2007-07-09 2009-01-15 Siemens Power Generation, Inc. Angled honeycomb seal between turbine rotors and turbine stators in a turbine engine
US20090189356A1 (en) * 2007-12-14 2009-07-30 Miklos Gaebler Sealing of at least one shaft by at least one hydraulic seal
US8444153B2 (en) 2007-12-14 2013-05-21 Rolls-Royce Deutschland Ltd & Co Kg Sealing of at least one shaft by at least one hydraulic seal
US20110002777A1 (en) * 2009-07-02 2011-01-06 General Electric Company Systems and apparatus relating to turbine engines and seals for turbine engines
US8317465B2 (en) 2009-07-02 2012-11-27 General Electric Company Systems and apparatus relating to turbine engines and seals for turbine engines
US20110229301A1 (en) * 2010-03-22 2011-09-22 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US20120091662A1 (en) * 2010-10-19 2012-04-19 General Electric Company Labyrinth seal system
US8876484B2 (en) 2011-08-05 2014-11-04 Hamilton Sundstrand Corporation Turbine blade pocket pin stress relief
US20140169972A1 (en) * 2012-12-17 2014-06-19 United Technologies Corporation Fan with integral shroud
US9617863B2 (en) * 2013-07-12 2017-04-11 MTU Aero Engines AG Gas turbine stage
US20150016985A1 (en) * 2013-07-12 2015-01-15 MTU Aero Engines AG Gas turbine stage
EP2886801A1 (en) * 2013-12-20 2015-06-24 Alstom Technology Ltd Seal system for a gas turbine and corresponding gas turbine
CN104727862A (en) * 2013-12-20 2015-06-24 阿尔斯通技术有限公司 Seal system for a gas turbine
US20150176424A1 (en) * 2013-12-20 2015-06-25 Alstom Technology Ltd. Seal system for a gas turbine
US10012101B2 (en) * 2013-12-20 2018-07-03 Ansaldo Energia Ip Uk Limited Seal system for a gas turbine
US20160305266A1 (en) * 2015-04-15 2016-10-20 United Technologies Corporation Seal configuration to prevent rotor lock
US10934875B2 (en) * 2015-04-15 2021-03-02 Raytheon Technologies Corporation Seal configuration to prevent rotor lock
WO2017155497A1 (en) * 2016-03-07 2017-09-14 Siemens Aktiengesellschaft Gas turbine blade tip shroud sealing and flow guiding features
CN107605543A (en) * 2017-08-14 2018-01-19 西北工业大学 A kind of dividing disc cavity configuration for wheel rim sealing
CN107605543B (en) * 2017-08-14 2019-05-10 西北工业大学 A kind of dividing disc cavity configuration for wheel rim sealing

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GB1008526A (en) 1965-10-27
DE1300347B (en) 1969-07-31

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